초록 ▼

In a gas turbine engine internal cooling system a high pressure turbine disc is cooled by an air flow directed at the face of the disc by nozzles formed in the inner platforms of the downstream guide vane annulus. A proportion of the cooling air collected in a plenum adjacent the disc is inducted in

In a gas turbine engine internal cooling system a high pressure turbine disc is cooled by an air flow directed at the face of the disc by nozzles formed in the inner platforms of the downstream guide vane annulus. A proportion of the cooling air collected in a plenum adjacent the disc is inducted into a second part of the vane internal cooling system is via a multi-pass system of passages is used to cool the vane internally and is exhausted through trailing edge apertures into the gas stream. Because of the variation of temperature and static pressure across the radial distance of the annular gas stream the air flow is metered internally and distribute between exit apertures along the height of the vane trailing edge to provide required cooling and exit flow.

대표청구항 ▼

1. An airfoil member for use with a gas turbine engine that includes an exterior side, an interior side, a disc disposed at the interior side, a turbine blade disposed on the disc, and a plenum defined adjacent the disc, the airfoil member being disposed adjacent the turbine blade, the airfoil membe

1. An airfoil member for use with a gas turbine engine that includes an exterior side, an interior side, a disc disposed at the interior side, a turbine blade disposed on the disc, and a plenum defined adjacent the disc, the airfoil member being disposed adjacent the turbine blade, the airfoil member comprising:a first cooling air passage having an entry orifice at the exterior side and an exit orifice to direct cooling air into the plenum; and a second cooling passage having an entry orifice that communicates with the plenum, a fluid flow restricting device, and a plurality of exit apertures, the fluid flow restricting device restricting fluid flow through at least one exit aperture of the plurality of exit apertures relative to at least one other exit aperture of the plurality of exit apertures.